再入段弹道导弹的最大可用舵偏角分析

Analysis on Maximum Available Rudder Deflection of Ballistic Missile in Reentry

导弹的控制能力是限制其制导控制系统性能指标的主要因素,如果未能充分考虑该因素的影响,会导致独立设计的制导律与姿态控制律的不匹配性,从而降低导弹初期设计工作的实用价值。考虑到最大可用舵偏角是再入段弹道导弹控制能力的一种直观体现,通过数学推导方式获得其解析表达式,并设计了与之对应的算法。利用风洞吹风试验数据,该算法可解算出一定飞行状态(包括高度、马赫数、攻角和侧滑角)下导弹各个舵的最大可用偏角,用于定点的静态分析或弹道的动态分析。借助于Matlab/Simulink计算机仿真手段,分析了某弹道内各个舵可用舵偏边界的变化规律,并绘制出相应的数据曲线,该曲线为导弹设计初期姿态控制系统的设计提供了约束条件和控制裕度的参考依据。

The control ability of missile is the main factor to limit the performance index of missile guidance control system. If the influ- ence of control ability is not fully considered, it will lead to unmatched relationship between guidance law and attitude control law, which are designed independently, and further reduce the practical value of initial design work. Considering the maximum available deflection of rudder is one kind of direct-view reflection for evaluating the control ability of ballistic missile in reentry, its analytical expression is obtained through mathematical derivation, and the corresponding algorithm is designed. Using data of the wind tunnel testing, the algorithm can calculate the maximum available deflection of each rudder in a certain flight condition （ including height, Mach number, attack angle and sideslip angle） ,and then is applied to static analysis at fixed point or dynamic analysis in whole trajectory. By means of Matlab/Simulink computer simulation, the changing law of available deflection boundary of each rudder is analyzed in one trajectory, and then relevant data curves are presented. The curves provide constraint conditions and references of control margin for the early design of missile attitude control system.